sts-47 space shuttle mission report

8/7/2019 STS-47 Space Shuttle Mission Report

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i _. _. _i ,_' ,' i . NASA-CR-1930S6".-- NSTS-08279

0 STS-47 I __o__,_os_' SPACESHUTTLE ,_oo_ ____ MISSION REPORTF(NASA-CR-I93056) STS-47 SPACE N93-25960 ISHUTTLE MISSION REPORT (Lockheed IEngineering and Sciences Co.) 38 p i

Unclas jG3/16 0163_75

October 1992 LIBRARYCOPYlANGLEYRESEARCHCENTER


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I!NSTS-08279

O STS-47SPACESHUTTLEMISSIONREPORT

/ P1 )ared by

Jr.LESC/FIi Evaluat andEngineeringOffice

Approvedby

MichaelEngleSTS-47LeadMissionEvaluationRoomManager

ODavid W.Manager, Flight Engineering Office


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O STS-47Tableof ContentsTitle Page

INTRODUCTION ....................... 1MISSION SUMMARY ..................... 2VEHICLE PERFORMANCE ................... 3

SOLID ROCKET BOOSTERS/REDESIGNED SOLID ROCKET MOTORS 3EXTERNAL TANK ..................... 4SPACE SHUTTLE MAIN ENGINE ............... 6SHUTTLE RANGE SAFETY SYSTEM .............. 6ORBITER SUBSYSTEM PERFORMANCE ............. 7

Main Propulsion System ............... 7Reaction Control Subsystem ............. 8Orbital Maneuvering Subsystem ........... 8Power Reactant Storage and Distribution Subsystem 8FuelCellPowerplantSubsystem........... 9AuxiliaryPowerUnit Subsystem............ i0 JHydraulics/WaterSprayBoilerSubsystem...... IIElectricalPowerDistributionand ControlSubsystem. iiPyrotechnicsSubsystem............... 12EnvironmentalControland LifeSupportSubsystem. 12SmokeDetectionand FireSuppression........ 13

O AirlockSupportSystemandTunnelAdapter ..... 13Avionicsand SoftwareSubsystems.......... 13CommunicationsandTrackingSubsystem ....... 14Structuresand MechanicalSubsystems........ 15Aerodynamics,Beating,and ThermalInterfaces . . . 17ThermalControlSubsystem ............. 17Aerothermodynamics................. 18


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STS-47 Table of Contents(Concluded) OTitle

PHOTOGRAPHICAND TELEVISIONANALYSES........... 25LAUNCHDATAANALYSIS 25ON-ORBITDATAANALYSIS ................ 25LANDINGDATA ANALYSIS ................ 25

Listof Tables

TABLEI - STS-47SEOUENCEOF EVENTS ........... 26TABLEII - STS-47PROBLEMTRACKINGLIST ......... 29TABLEIII- STS-47SPACELAB-JEXPERIMENTSLISTING .... 32

O


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O INTRODUCTION The STS-47SpaceShuttleProgramMissionReportprovidesa summaryof theOrbiter,ExternalTank (ET),SolidRocketBooster/RedesignedSolidRocketMotor(SRB/RSRM),and the SpaceShuttlemain engine(SSME)subsystemperformance. duringthefiftiethSpaceShuttleProgramflight;and the secondflightof theOrbitervehicleEndeavour(OV-105).In additionto theEndeavourvehicle,theflightvehicleconsistedof an ET whichwas designatedET-45 (LWT-38);threeSSME'swhichwere serialnumbers2026,2022,and2029andwerelocatedin

positionsI, 2, and 3, respectively;and two SRB'swhichweredesignatedBI-053.The lightweight/redesignedRSRM thatwas installedin theleftSRBwasdesignated360L026A,and theRSRM thatwas installedin therightSRBwas360g026B.\ The STS-47SpaceShuttleProgramMissionReportfulfillsthe SpaceShuttleProgramrequirement,as documentedin NSTS07700,VolumeVIII,AppendixE, whichstatesthateachmajororganizationalelementsupportingtheProgramwill reportthe resultsof itshardwareevaluationand missionperformanceplus identifyall

relatedin-flightanomalies.The sequenceof eventsfor theSTS-47missionis shownin TableI, and theOfficialOrbiterand GFE ProjectsProblemTrackingListis shownin TableII.In addition,the reportalsodiscusseseachOrbiter,SSHE,ET,and SRB/RSRMsubsystemanomalyin theapplicablesectionof thereport,and a referenceto

O theofficialassignedtrackingnumberis mentionedin the bodyof thereport.Additionally,all timesin the textof thereportaregivenin bothGreenwichmean time(G.m.t.)and missionelapsedtime(MET).The primaryobjectiveof theSTS-47flightwas to successfullyperformtheplannedoperationsof theSpacelab-J(SL-J)payload[containing43 experimentsof which34 were providedby theJapaneseNationalSpaceDevelopmentAgency


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MISSIONSUMMARY QThe STS-47mission was launchedat 256:14:23:00.010G.m.t. (10:23:00a.m.e.d.t.on September12, 1992) from Launch Complex39B at Kennedy Space Center (KSC).STS-47 was a Spacelab-Jmission,a joint venture betweenNASA and the NASDA ofJapan. iApproximately7 hours prior to launch and duringhydrogen fast-fill,thehydrogen concentrationin the aft compartmentreached 550 ppm, exceedingtheLaunch Commit Criteria (LCC)limit of 500 ppm. The leakwas in the low-pressureportion of the system and the leak rate was not expected to increasesinceflight pressureswere the same level as thoseexperiencedduring fast-fill.Based on this logic, a waiver was approved. During replenish,the hydrogenconcentrationdropped below the LCC limits.The improved auxiliarypower unit (IAPU) 3 fuel test line temperatureexceededthe LCC lower limit of 48F. A waiver was approvedwhich allowed thetemperatureto go down to 43F; however, the lowest temperatureexperiencedwas46F.All SSME and RSRM start sequencesoccurred as expectedand the launch phaseperformancewas satisfactoryin all respects. First stage ascent performancewas normal with SRB separation,entry, deceleration,and water impactoccurringas anticipated. Both SRB's were recovered. Performanceof the SSHE's,ET, andmain propulsionsystem (MPS)was also normal, withmainenginecutoff(MECO)occurringatapproximately513.6secondsafterlift-off.A determinationofvehicleperformancewasmadeusingvehicleaccelerationandpreflightpropulsionpredictiondata. From these data, the average flight-derivedengine specificimpulse (Isp) determined for the time period between SRB separationand start of3-g throttlingwas 452.2 secondsas compared to an average engine tag value of452.27seconds.


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O RCS vernier thruster L5D chamber withexperienced degraded pressure (80psiall0 psia nominal). Mission trend data indicated a slow degradation from103 psia to 76 psia with some recovery on longer burns. A 4.5-second hot-fire

. test, followed by a 5-second rate-damping firing of L5D, was performed with nosignificant improvement in chamber pressure. Following the flight controlsystem (FCS) checkout, the chamber pressure on RCS thruster L5D returned to nearnominal values.4The FCS checkout was completed at 262:09:57:57.64 G.m.t. (05:19:34:57.64 MET)using IAPU 3 and all systems operated satisfactorily. IAPU 3 operation wasextended to 12 1/2 minutes to verify proper cooling by WSB 3 on bothcontrollers. USB cooling was attained at nominal temperatures.The RCS hot-fire test was performed at 264:06:13 G.m.t. (07:15:50 MET). Allthrusters operated nominally except L3A which had been deselected since early inthe mission.Because of potentiallyunsatisfactoryweather at KSC, the Orbiter was waved offfor the first landingopportunityon flight day 8. Weather conditionswereacceptablefor the secondlandingattempt and the decisionwas made to land atKSC on the secondopportunity.Both payload bay (PLB) doors were closed nominallyby 264:09:15:56G.m.t.(07:18:52:56MET). The deorbitmaneuverwas performedat 264:11:52:20.2G.m.t.(07:21:29:20.2MET). The maneuverwas approximately153.0 seconds in duration

O and the differentialvelocity (_V) was 262.4 ft/sec. Entry interfaceoccurredat 264:12:21:43G.m.t.(07:21:58:43MET).Main landinggear touchdownoccurred at KSC on concreterunway 33 at264:12:53:22G.m.t.(07:22:30:22MET),followedbyOrbiterweight-on-wheelsonesecond later. The Orbiterdrag chute was deployedsatisfactorilyat264:12:53:30.7G.m.t. (07:22:23:30.7MET) which was prior to nose gear


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Arequirementsweremet withamplemargins. All electricalfunctionswereperformedproperly. No SRB or RSRM LCC violationswerenotedduringthecountdown.One Operationsand MaintenanceRequirementsand SpecificationsDocument(OMRSD)violationoccurredduringtheOrbiterfuelcellactivationsequence.The SRB powertransferbussesexperienceda slightover-voltagesimilarto thatobservedon STS-46. The OMRSDlimitof 32.0Vdc was exceededby0.189Vdc on bothA busses,and by 0.106Vdc and 0.023Vdc on therightand leftB busses,respectively.Thisconditionwas officiallywaivedpriorto lift-off. Powerup and operationof all case,igniter,and field-jointheaterswereaccomplishedroutinely.All RSRM temperaturesweremaintainedwithinacceptablelimitsthroughoutthecountdown.For thisflight,theheatedgroundpurgeinthe SRB aft skirtwas not neededto maintainthecase/nozzlejointand flexiblebearingtemperatureswithintherequiredLCC ranges;however,it was activatedat T-15 minutesto inerttheaft skirtareaof any hydrazine.The SRB flightstructuraltemperatureresponsewas as expected.Postflightinspectionof therecoveredhardwareindicatedthattheSRB thermalprotectionsystem(TPS)performedproperlyduringascentwithvery littleTPS acreageablation.Preliminarydataindicatesthattheflightperformanceof bothRSRM'swas wellwithintheallowableperformanceenvelopes,and was typicalof the performanceobservedon previousflights.The meanbulktemperaturewas 82Fat lift-off.KeyRSRM propulsionperformanceparametersare presentedin the tableon thefollowingpage. @Both SRB'sweresatisfactorilyseparatedfromtheET at T + 124.0seconds,andseparationsubsystemperformancewas normalwithall boosterseparationmotors(BSM's)expendedand all separationboltssevered. Nosecap jettison,frustumseparation,and nozzlejettisonoccurrednormallyon eachSRB. The entryanddecelerationsubsystemsperformedproperlyon bothSRB's. RSRMnozzlejettison


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O RSRM PROPULSIONPERFORMANCEParameter Left motor, 82F Right motor, 82FPredicted Actual Predicted Actual

Impulse ga_es1-20, I0_ ibf-sec 66.08 66.18 66.28 66.11' 1-60, I0. ibf-sec 175.95 176.25 176.40 176.39I-AT, l0b ibf-sec 296.64 295.91 296.81 297.16

Vacuum Isp, Ibf-sec/ibm 268.6 267.8 268.6 268.8Burn rate, in/sec @ 60 F 0.3673 0.3687 0.3677 0.3673at 625 psiaEvent times,secondsIgnition interval 0.232 N/A 0.232 N/AWeb timea 109.0 109.0 108.7 109.0Separationcue, 50 psia 118.7 118.0 118.4 118.9Action time 120.7 120.1 120.5 121.3

PMBT, OF 82.0 82.0 82.0 82.0Maximum ignition rise rate, 90.4 N/A 90.4 N/Apsia/10ms

O Decay time, seconds 2.8 2.8 2.8 3.1(59.4 psia to 85 K)Tailoffimbalance Predicted Actual.Impulsedifferential, N/A 629.4D


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forwardof the LH2 splice closeout,centeredbetween the -Y and +Y bipods in thetwo-toneTPS area. Detailedphotographicanalysesshow the divot to beapproximately16 inches in diameterwith an indeterminabledepth. This ET usedthe older two-toneTPS configuration(CPR-488over BX-250with an isochemadhesive). Historical problemswith the two-toneconfigurationoccurred duringthe manufacturingphase and extensiveeffortshave been made to resolve thecondition. Numerous possible causes of the divot on this ET were postulated,but no positive cause of the divot could be identified. Consequently,this isan unexplainedanomaly and an isolatedincident.

SPACE SHUTTLEMAIN ENGINEAll SSME parametersappeared to be normal throughoutthe prelaunchcountdown_and were typicalof prelaunchparametersobserved on previous flights. Launchground support equipment (GSE)providedadequate control for the SSME'sduringlaunch preparation. All engine-relatedconditionsfor engine start wereachieved at the proper time, all LCC were met, and engine start and thrustbuildup were normal.Flight data indicates that SSME performanceduring mainstage,throttling,shutdown and propellantdump was well within specifications. All threeenginesstarted and operated normally. High pressureoxidizer turbopump(HPOTP)andhigh pressure fuel turbopump(HPFTP) temperatureswere well within specificationthroughoutengine operation.The SSME controllersprovided proper controlof the engines throughoutpowered _I_flight. Engine dynamicdata generally comparedwell with previous flight andtest data. All on-orbitactivitiesassociatedwith the SSME'swere accomplishedsuccessfully. One anomalywas identifiedin the SSKE data that occurred duringthe SSME start and mainstagephases,when SSME I (unit no. 2026) HPOTP secondaryturbine seal cavity pressure (channelA) exhibitednumerousdownwardspikes(Flight Problem STS-47-E-1). An in-depthdata review revealedapproximately


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Priorto SRB separation,theSRB S&Adeviceswere safed,and SRBsystempowerwas turnedoff,as planned. The ET systemremainedactiveuntilET separationfrom the Orbiter.ORBITERSUBSYSTEMSPERFORMANCE

. Main Propulsion SystemThe overallperformanceof theMPSwas excellent.All pretankingpurgeswereproperlyperformed,and loadingof LO^ and LH^was completedduringthelaunchcountdownwithno stop-flowsor reverts.ThezMPSheliumsystemperformedsatisfactorily.Therewereno OMRSDviolations.Approximately7 hourspriorto launchandduringhydrogenfast-fill,thehydrogenconcentrationin the aft compartmentreached550 ppm,exceedingtheLaunchCommitCriteria(LCC)limitof 500 ppm (FlightProblemSTS-47-V-01).The 60-ppmincreasein theaft compartmentconcentrationassociatedwith thestartof therecirculationpumpswas normal,indicatingthattheleakin theaftcompartmentwas withinthelow-pressureLH2 system. Sinceascentpressuresinthissystemare comparableto thoseexperiencedduringfast-fill,it wasconcludedthattheleakwouldnot increaseduringascent,and thatthemaximumconcentrationof 550 ppmwas safeto flyand comparablewith OV-IO2experie,ce.Additionally,experiencehas shownthateachvehiclehas a uniqueleakagesignature,with0V-102havinga 600-ppmLCC. 0V-105stillhasa verysmallexperiencebase. Basedon thislogic,a waiverwas approved.Duringreplenish,thehydrogenconcentrationdroppedbelowthe LCC limits.The aft compartmenthydrogenconcentrationdroppedto 75 ppm afterhydrogenloadingproceededintotoppingand theET was vented. Aft compartmentconcentrationsremainedbelow100 ppm forthe durationof loading.A comparisonof the calculatedpropellantloadsat theend of replenishversus


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was requestedto terminatethe sequenceand shut down the IAPU'sbecause opening ithe TVC isolationvalves would have resultedin a large step command to theactuators that may have damaged the actuatorsor hydrauliclines.ReactionControl Subsystem

The RCS performancewas acceptableand the subsystemmet all requirements;however, two thrusteranomalieswere noted. The RCS was also used to performDTO 251 - Entry AerodynamicControlSurfaceTest AlternateElevon Schedule.RCS propellant consumptionfor the missionwas 3917.2lb.During the ET separationmaneuver at 256:14:33G.m.t. (00:00:I0MET), RCSprimary thrusterL3A failed to operate (FlightProblem STS-47-V-03). Data .,Iindicatedlow chamberpressure (


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48.3hours. A totalof 281.1ib of hydrogenand 2331.9Ib of wasoxygenconsumedduringthemissionwith 101.8ib of the totaloxygensuppliedto thecrewfor breathingpurposes.The PRSDoxygentank4 heatercontrolpressurebeganreadingoff-scalelow at256:15:30G.m.t.(00:01:07MET) (FlightProblemSTS-47-V-06),but the indicationreturnedto normalduringentry. Thisconditiondid not impactoperations,asthe tank3 heatercontrolpressuretransducerwas usedto controlthe tank4heater. Oxygentanks3 and 4 suppliedthe fuelcellsthefirstdaywithnoimpactfromthetank4 heatercontrolpressure.For troubleshootingpurposes,oxygentank4 was operatedindependentof oxygentank3, decouplingthecontrollogicof theoxygentanks3 and 4 heatercontrolboxes. The oxygentank4heatersremainedon even thoughthebackuptankpressuremeasurementindicaaedthatthe tankpressurewas abovetheheater-offvalue. Thisconditionverifiedthat theoxygentank4 heatercontrollogicwas sensing515 psia (off-scalelow)heatercontrolpressure.Oxygentanks3 and4 wererecoupledfortheremainderof the mission.The measurementbeganperformingsatisfactorilyafterterminalarea energymanagement(TAEM).

Fuel Cell Powerplant SubsystemThe fuel cell powerplantsubsystemperformedsatisfactorilythroughoutthemission. A total of 3249.7 kwh of energy was producedwith an average powerlevel of 17.1 kW/556.2amperes. The fuel cells produced2511 ib of water duringthe mission.The first fuel cell purge was performedat 23 hours MET, with additionalpurgesperformedapproximatelyevery 48 hours for the remainderof the mission. Afinal purge was made within 8 hours of entry. No fuel-cellvoltage degradationsgreater than 0.i V were seen betweenpurges.At approximately256:17:53G.m.t. (00:03:30MET), the fuel cell water overboard


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AAuxiliary Power Unit Subsystem g

The IAPU performance was nominal with the exception of two anomalies, neither ofwhich had an impact on the satisfactory operation of the IAPU's. The followingtable presents run times as well as propellant consumption for the IAPU's.

IAPU 1 (S/N 303) IAPU 2 (S/N 401) IAPU 3 (S/N 207)Flight Phase Time, Fuel Time, Fuel Time, Fuel

min:sec consumption, min:sec consumption, min:sec consumption,lb lb lbAscent 19:48 48 19:48 48 17:56 45 .+sFCS checkout 12:38 34Entry_ 58:35 115 80:21 148 58:31 117Totala 78:23 163 100:09 196 89:05 196

aTheIAPU'swereoperatedfor approximately14 minutes29 secondsafterlanding.Prior to launch, IAPU 3 fuel test line temperature exceeded the LCC lower limitof 48F (Flight Problem STS-47-V-02). Since heater cycling had been verifi4d, awaiverwas approvedthatallowedthe temperatureto go down to43F,whichisthe minimum temperature to preclude freezing prior to the time that the crew canactivatethe heatersafterorbitalinsertion;however,the lowesttemperatureexperienced was 46F. During ascent, the IAPU 1 fuel test line temperature fellbelow the FDA limit and an alarm was sounded. This condition is explainable asthe heaters are normally not powered for ascent.IAPU 3 was shutdown early after the completion of ascent when the bearingtemperature reached 335F because WSB 3 was not providing any cooling. Adiscussion of the WSB cooling anomaly is contained in the Hydraulics/Water Spray


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O gearbox repressurlzations during entry: one at theIAPU 3 experienced threestart of entry, one about 16 minutes later, and the third occurred about 32minutes after IAPU start. No FDA limits were violated and all other lubrication. system parameters remained nominal. The gearbox pressure increased duringatmospheric flight and while on the runway, indicating that the gearbox pressurewas leaking through the turbine seal. This condition has occurred on theo previousflightsof the IAPU's,andappearsto be characteristicof theIAPU's.

Hydraulics/Water Spray Boiler SubsystemThehydraulicssubsystemoperationwas nominalthroughoutthe flightandWSBsubsystemoperationwas acceptablewith threeanomaliesnoted.During ascent, WSB 1 and 3 displayed anomalous operation with WSB 1 exhibiting adelay in IAPU 1 lubrication oil cooling (Flight Problem STS-47-V-05), and WSB 3exhibiting no cooling until just prior to the early shut down of IAPU 3 (FlightProblem STS-47-V-07). VSB 1 did not begin spraying until the IAPU 1 lubricationoil temperature reached 280F. Once cooling started, the USB over-cooled (below250F) to 236F before beginning to operate properly. The File IX in-flightcheckout limit of 275F was violated; consequently, a WSB 1 checkout as well asa hot-oil flush were performed during postflight turnaround activities becausethelubricationoil temperatureexceeded275F. In addition,the _SB 1regulator outlet pressure steadily increased throughout the flight, indicatingthatleakagepast theregulatorwas occurring(FlightProblemSTS-47-V-20).

O Duringascent,WSB 3 failedto coolon controllerA, and whenswitchedtocontrollerB, the temperaturecontinuedto climbto 335Fwhen a decisionwasmade to shutdownIAPU3 early. CoolingbeganjustbeforeIAPU3 was shut downand for about2 minutesmorebeforeWSBspraycoolingwas shutoff. The WSBperformedsatisfactorilyon controllerA andB duringtheFCS checkoutas wellas on controllerB duringentry. All of theseconditionsare indicativeofwaterspraybar freeze-upduringascent.


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PTrotechnicsSubsTstem 0The pyrotechnics subsystem performed all required functions in a satisfactorymanner. The drag chute mortar and retractor performed as expected anddeployment and jettison of the drag chute was satisfactory.

EnvironmentalControland LifeSupportSubsystemThe atmosphericrevitalizationsystem(ARS)performancewas nominal. The airand watercoolantloopsperformancewas normal. The CO. partialpressurewasmaintainedbelowthehighestacceptablelevelof 4.70m_z Hg. The cabinairtemperatureand relativehumiditypeakedat 84Fand 40 percent,respectively.The avionicsbaysI, 2, and 3 air outlettemperaturespeakedat I06F,I07F|and 87.8F,respectively.Also the avionicsbays I, 2, and 3 watercoldplatetemperaturespeakedat 87.5F,91.5F,and81.2F,respectively.The cabinhumiditysensorreadingstuckat a constantlevelat 264:13:13G.m.t.(07:22:50MET) (FlightProblemSTS-47-V-15).This samesignatureoccurredonSTS-49. Likewise,thehumiditysensordid not respondto postflighthumiditychanges. Troubleshootingshowedthat themanufacturer'splasticwrappingaroundthehumiditysensorwas stillin place,thuspreventingthemeterfromgivingatruereading. Afterremovingthewrapping,a shortretestshowedthesensortobe ingoodworkingorder.Whileinstallingthefilterfor DTO 647 (WaterSeparatorFilterPerformanceEvaluation),the crewnotedthatthewaterlinefor theliquidcoolingandventilationgarmentand thewaterchillerwas lackinginsulationandexperiencingwatercondensation.Drawingsshow thatthiswaterlineshouldbeinsulated.KSC investigatedthisconditionafterlandingand thenecessarycorrectiveactionwas taken.All pressurecontrolsystem(PCS)operatingparametersremainedwithinnormal


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O The supply and waste water systems performed nominally. All assigned in-flightcheckout requirements were completed. Supply water was dumped through the FES,and the supply water dump line temperature was maintained between 71 and 99Fwith the operation of the line heater. No overboard supply water dumps wererequired.Two waste water dumps were performed satisfactorily. The average dump rate was1.95 percent/minute (3.2 ib/hr). The waste water dump line temperature wasmaintained between 55 and 80F, while the vacuum vent llne temperature wasmaintained between 56 and 80F.The waste collection system (WCS) performed nominally until flight day 5. Inaddition to normal WCS operations, the fan separator had been used to provid@airflow to the urine monitoring system. At 262:05:19:45 G.m.t.(05:14:56:45 MET), fan separator I exhibited stall currents similar to thoseobserved when the WCS is flooded. The crew switched to fan separator 2 and usedit successfully for a short period of time before performing a fan separator 1clearing procedure, after which fan separator 1 was used for the rest of themission. The crew allowed fan separator I to run for extended periods of timeup to 3 hours 20 minutes following the failure in an attempt to dry out the fanseparator. As a result, fan separator 1 start-up times reduced to a nominal4 seconds as the mission progressed.A redesign of the fan separator is currently in progress to make the fanseparator less likely to flood in-flight. Design improvements include a

O re-designed bowl with dividers to prevent splashing and liquid bypass, and adelayed shut down mechanism to ensure that all liquid is pumped out prior to theshut down. The redesign will be implemented in February 1993.Smoke Detectionand Fire SuppressionSubsystem

All smoke detectionsubsystemparametersremainedwithin normal limits and the


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thermallyinduced.The testinvolvedrunningfiveself-testsof the-Z startracker,then powering down the star trackerfor two hours, and then runningadditionalself-testsafter the unit was repowered. During the pre-powerdowntesting, the star tracker failed the secondself-test. This failureoccurred inan expectedmanner (a known failuremode) and it was a differentfailure modefrom the two failures that occurredearlier in the mission. A decision was madeto stop the testingafter the failurewas identified.The data processingsystem flight softwareand hardwareperformednominally.The operationalinstrumentation/modularauxiliarydata system hardwareencounteredthree anomalies,none of which had any impact on the successfulcompletionof the mission. The anomalieswere:

a. SSME LH2 inlet pressure indicatedoff-scalelow. This problem isdiscussed in the Main PropulsionSystem Sectionof this report.b. IAPU 3 test line temperature2 trendedlow during the prelaunch timeframe. This problem is discussedin the AuxiliaryPower Unit section of this

report.c. Left-handoutboard tire pressure showed excessivebias with respect'tothe new calibrationcurve used. This anomaly is discussedin the StructuresandMechanicalSubsystems sectionof this report.

Communicationsand Trackin_ Subsystem VThe communicationsand trackingsubsystemperformednominally throughoutthemission with some minor problems that are discussedin the followingparagraphs.Early in the mission, severalground stationsreported a weak UHF downlinksignal, while the Orbiter received strongLr_Fuplink signals from the ground


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(CCTV) camera A was noted to a spot.Closed-circuit television have small burnThis was a known condition prior to flight that did not affect performance ofthe camera during the entire mission. Also, during a real-time downlink ofvideo from CCTV camera D, horizontal jitter was noted (Flight ProblemSTS-47-V-18). This jitter was also noted on a previous transmission. Thejitter effect occurred only during the first few minutes after camera power-up,after which the camera operated nominally. Camera D was used for the remainderof the mission.The crew reported that the tens digit of the Ku-band range rate/azimuth displaywas blank (Flight Problem STS-47-V-II). A lamp test was performed and all LEDsegments illuminated.During entry, the Tactical Air Navigation (TACAN) bearing indication experienceda 40-degree excursion for approximately 13 seconds (Flight Problem STS-47-V-19).Postflight testing will be performed on this TACAN using the bearing simulator.

Structures and Mechanical SubsystemsThe structures and mechanical subsystems performed satisfactorily. The nominallanding and braking data are shown in the table on the following page.The prelaunch side hatch electrical continuity check after hatch closurerevealed that two of the continuity measurements were unsatisfactory. Aprocedure, which involved reopening the hatch and visually checking the latches,verified that the latches were over-center. The same procedure was used priorto the first flight of OV-105 when the same condition was experienced. Thehatch was again closed and the continuity checks were completed withsatisfactory results.The left-hand outboard main tire pressure sensors I and 2 were biasedexcessively with respect to the new calibration curve that had been used (Flight


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LANDING AND BRAKING PARAMETERS OFrom

Parameter threshold, Speed, Sink rate, ftlsec Pitch rate,ft keas deglsecMain gear touchdown 2458 204.6 "I.0 nlaNose gear touchdown 7651 133.9 nla 1.92

Braking initiation speed II0.I knots (keas)Brake-on time 29.6 secondsRollout distance 8,547 feetRollout time 50.9 secondsRunway 33 (concrete) at KSCOrbiter weight at landing 220,097 ib

Brake sensor location Pressure, Brake assembly Energy,psia million ft-lbILeft-hand inboard 1 1116 Left-handoutboard 19.53Left-hand inboard 3 1140 Left-handinboard 17.86Left-hand outboard 2 1272 Right-handinboard 27.02Left-hand outboard 4 1224 Right-handoutboard 24.42Right-hand inboard 1 1728Right-hand inboard3 1656Right-handoutboard 2 1476Right-handoutboard 4 1416


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O Aerodynamics, Heating, and Thermal InterfacesThe ascent and entry aerodynamics were satisfactory with no problems observed in

the data. During entry, DTO 251 - Entry Aerodynamic Control Surfaces Test - wascompleted except for programmed test input (PTI) 3 which could not be performedbecause a required roll reversal maneuver occurred during the planned Machwindow for PTI 3. There was no indication of abnormal aileron trim excursionsduring the high negative elevon settings as had been experienced on a previousflight.The integrated aerodynamic and plume heating on the vehicle during ascent wasnominal with no unexpected conditions noted. Likewise, the heating during entrywas also nominal and within the TPS limits.The thermal interface temperatures were maintained within the specified limitsand no LCC temperature violations occurred.

Thermal Control Subsystem

The performance of the thermal control subsystem was nominal during all phasesof the mission with all Orbiter subsystem temperatures being maintained withinacceptable limits. Three temperature sensor anomalies occurred, but none ofthese impacted the mission. These anomalies are as follows:

a. The IAPU 3 fuel test line temperature sensor 2 violated the LCC lowerO limit of 48F. This anomaly is discussed in the Auxiliary Power Unit section ofthis report.

b. Shortly after ascent, the IAPU I system A drain line temperature sensor2 cycled at 46"F, which is below the FDA limit of 48"F. This anomaly isdiscussed in the Auxiliary Power Unit section of this report.


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Aerothermodynamics @Acreage heatingwas nominal duringentry with all structuraland TPStemperatureswithin the experiencebase. Local heatingwas also normal and theTPS damage was within the experiencebase. No effectswere expected or notedfrom the performanceof the PTI's as a part of DTO 251.

Thermal ProtectionSubsystemThe thermal protectionsubsystem (TPS)performancewas nominal, as compared toprevious flightsof the Space Shuttle fleet. This conclusionis based onstructural temperatureresponse data and on some tile surface temperaturemeasurements. The overall boundarylayer transitionfrom laminar to turbulentflow was non-symmetric. Transitionoccurredat 1210 seconds after entryinterfaceon the aft portion of the vehicle (X/L = 0.6) and at 1320 seconds onthe forwardside of the vehicle (X/L= 0.3). The time of transitionwas thelatest for the forward sectionof the vehicle since the start of Space Shuttleflights.The number of hits was much less than averagewhen comparedwith previousmissions. From a debris damage standpoint,STS-47representsone of the best inthe Space Shuttle Program. The detailedevaluationand analysisof the TPS'wIIIbe documented in a NASA TechnicalMemorandum- TM 107553.During the prelaunchinspection,the Ice InspectionTeam detected a scratch onthe upper surface of the left wing reinforcedcarbon-carbon(RCC) panel 9,approximatelyone-third the distance back from the leadingedge. The scratch isa turnaroundand reuse issue, and was not a safety-of-flightissue.The Orbiter sustaineda total of 107 hits of which 11 had a major dimension ofone inch or greater. This total does not include the numeroushlts on the baseheat shield that were attributed to SSME vibrationlacousticsand exhaust plume


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Damage to shield tiles was less than average. The SSMEthe base heat 1dome-mounted heat shield (DMHS) closeout blanket splice exhibited minor frayingat the 6:00 o'clock position. All of the remaining DMHScloseout blankets werein excellent condition.The redesigned, mechanically attached ET door thermal barriers performed welland showed no signs of degradation. The room temperature vulcanizing (RTV)shimswhichhad beeninstalledto increasethe environmentalpressuresealcontactalsoshowedno signsof deterioration.No evidenceof flowpathswasfound,indicatingthatthedoorhad sealedproperly.At 262:18:49G.m.t.(06:04:26MET),the crewdownllnkeda descriptionof thethermalbarrierin theupper/lowerspeedbrakesplitline. The barrierwasstandingout approximately1 inchfromtheoutermoldlinewithroomtemperaturevulcanizing(RTV)materialshowingforthe fulllengthof the thermalbarrier(FlightProblemSTS-47-V-13).Evaluationshowedthat thisconditionposednoproblemfor theremainderof the flight. The postflightinspectionof therudderspeedbrakesplitline thermalbarriershowedthebarrierto be protrudingslightlyand someevidenceof minorfrayingwas alsonoted. However,thethermalbarrierdid not appearto besignificantlydamagedor deformed.Orbiterwindows3 and 4 exhibitedlighthazingwitha fewstreaks. HazingOntheotherwindowswas lessthanusual. Surfacewipeswere takenfromallof theforwardfacingwindows(I through6) forlaboratoryanalysis.Twenty-eighttileimpactsites(includingthreelargerthanone inch)were notedon theperimetertilesaroundwindows2 through6. All of thesehitswereshallowin depthandmay havebeencausedeitherby theRTV materialused to bondpapercoversto theforwardRCS nozzles,or by exhaustproductsfromtheSRBboosterseparationmotors,or by ice/TPSdebrisfromtheET LO2 tank.The runwayinspectionwas completedimmediatelyfollowingthe landing,and theonlyunexpectedflighthardwarefoundwere numerouspiecesof tilematerial


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GOVERNMENT FURNISHED EOUIPMENT/FLIGHT CREW EOUIPMENT OAll flight crew equipmentoperated nominally. The galley package in-placemicroswitchwas very sticky in its operation(FlightProblem STS-47-V-24). Thegalley was returned to JSC for troubleshootingand disassembly. Disassemblyofthe package-in-placemicroswitchassembly revealedthata layer of sediment hadformedon the stop for the level mechanismpreventingthe package-in-placeswitch lever from returningcompletely. After removingthe sediment,thepackage-in-placeswitch functionedproperly.During the STS-52 (OV-I02) ShuttleOrbiterRepackagedGalley (SORG)functionaltestatKSCon September18,1992,a failureof thegalleyhotwatertank _,ioccurredin which two of the six electricallyresistiveheater strips debondedfrom the water tank heat sink. Investigationinto the conditionrevealedadesign deficiencyin the manner that the six strips are bonded to the heat sink.As a result of this design deficiency,a decisionwas made on flight day 8 toturn the power off on the STS-47galley, includingthe water tank heaters andthe oven. In addition,a decisionwas made to fly low-usageheater strips fromthe originalgalley water tanks on STS-52,STS-53,and STS-54. Newly designedheater strips that correct the design deficiencywill be flown beginningwithSTS-55.During prelaunchoperationsafter the crew entered the Orbiter,the MissionSpecialist3 launch/entrysuit (LES)oxygenhose became disconnectedfrom thesuit (Flight Problem STS-47-V-25). The hose could not be relocated,andconsequently,was not reconnectedfor ascent. The crew persondecided to usethe emergency oxygen if conditionsarose that requiredthe use of breathingair.

CARGOINTEGRATION


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O maximum number of Japanese scientists to participate in space-based research, totrain in mission operations, and to demonstrate the effective use of the spaceenvironment for research. Spacelab-J was also the first space flight for aNASDA payload specialist. For NASA, nine experiments allowed the expansion ofknowledgegainedon previousmissionswhilehelpingto preparefor researchonSpaceStationFreedom.

" Scienceoperationsbeganwhen the crewinitiatedSpacelabactivationat256:16:34G.m.t.(00:02:11MET),with experimentationbeginningalmostimmediatelyto ensuremaximumexposureto themicrogravityenvironment.Spacelab-JoperationswereconcludedwithSpacelabdeactivationat264:01:43G.m.t.(07:11:20MET).

SHUTTLEAMATEURRADIOEXPERIMENTDuringthecourseof the mission,theShuttleAmateurRadioExperiment(SAREX)was used tomake contactswithschoolsin theUnitedStatesandAustralia.Over30 studentquestionswereansweredby variouscrewmemberson thisseventhflightof the SAREX. The schoolscontactedwere:

a. AustralianMaritimeCollege,Launceston,TasmaniaAustralia;b. WesleyCollege,SouthPerth,WesternAustralia;c. Del-MarMiddleSchool,SantaCruz,California;

O d. McKinleyHigh School,Honolulu,Hawaii;e. FlindersUniversity,BedfordPark,Australia;f. CaryHighSchool,Cary,NorthCarolina;and


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c. G-300 - Sponsored by the Matra Marconi Space/Laboratorie De GenieElectrlque De Paris of Paris, France.d. G-330 - Sponsored by the Swedish Space Corporation of Solna, Sweden.e. G-482 - Sponsored by the Spar Aerospace Limited of 0uebec, Canada.f. G-520 - Sponsored by the Ashford School of Kent, England.g. G-521 - Sponsored by the Canadian Space Agency of Ottawa, Canada.h. G-534 - Sponsored by the NASA Lewis Research Center of Cleveland, Ohio.i. G-613 - Sponsored by the University of gashington of Seattle,

Washington.ISRAELI SPACE AGENCY INVESTIGATION ABOUT HORNETS

The ISAIAH was the first experiment/investigation that has been flown for theIsraeli Space Agency, and was to investigate the effect of weightlessness oncombs built by oriental hornets.On flight day 2, the humidity in the experiment elevated to 99 percent, whichwas deemed unacceptable. The use of the suit fan attached to the left air inletof the unit was initiated, and the humidity was reduced to 94 percent. However,thehumiditybeganto rise immediatelyafterthesuitfanwas removed.An IFM procedureto removeone smallscrewon eachsideof the payloadwasaccomplishedafter SafetyPanelapproval. Monitoringevery15 minuteswascontinued for one hour and then once every two hours. Humidity began droppingin the experiment and stabilized at 78 percent within 24 hours. Nominaloperation returned after the 2-hour monitoring cycle.


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O DEVELOPMENT TEST OBJECTIVESDTO 251 - Entry Aerodynamic Control Surfaces Test - Alternate Elevon Schedule(Test 3) - This DTO was completed during entry except for one PTI of the sixplanned. PTI 3 was scheduled at the same time as a roll reversal maneuver,which took precedence over the PTI, and the PTI was not performed. The ailerontrim was as expected for each PTI performed.DTO 301D - Ascent Structural Capability Evaluation - This was a data-only DTOand the data were given to the Sponsor for evaluation.DTO 305D - Ascent Compartment Venting Evaluation - This was a data-only DTO andthe data were given to the Sponsor for evaluation.DT0 306D - Descent Compartment Venting Evaluation - This was a data-only DTO andthe data were given to the Sponsor for evaluation.DTO 307D - Entry Structural Capability - This was a data-only DTO and the datawere given to the Sponsor for evaluation.DTO 312 - ET TPS Performance - Good photographic data were obtained from theflight deck as well as from the two cameras located in the ET/Orbiter umbilfcalwells. A detailed evaluation of the ET photography is contained in a reportpubished by the DTO sponsor.

O The Payload Commander, using the 70-mm camera with a 250-mm lens, obtained 70excellent-quality photographs of the ET after separation from the Orbiter. Thefirst picture was taken 4 minutes 40 seconds after ET separation, and thedistance to the ET was calculated to be 1,018.3 meters. The last picture wastaken 13 minutes 53 seconds after separation, and the calculated distance to theET was 3,862.86 meters. The separation velocity between the Orbiter and ET wascalculated to be 5.14 meters/second.


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DTO 623 - Cabin Air Monitoring - The cabin air monitoring DTO equipment wasactivated at 256:22:43 G.m.t. (00:08:20 MET), and the data are being evaluatedby the sponsor.DTO 647 - Water Separator Filter Performance Evaluation - The filter for DTO 647was installed and the filter initially appeared to not be wicking the water asexpected; however, later observations showed very satisfactory operations.Filter operation from flight day 3 through flight day 7 was nominal.DTO 651 - Cycle Ergometer Hardware Evaluation - All scheduled evaluations of thehardware were completed successfully.DTO 655 - Foot Restraint Evaluation - The foot restraints were evaluated by,,erewmembers during the flight. The sponsor has received this information and theDTO is being evaluated.DTO 663 - Acoustical Noise Dosimeter Data - Data were collected for this DTO,and are being analyzed by the sponsor.DTO 665 - Acoustical Noise Sound Level Data - Data were collected for this DTO,and are being analyzed by the sponsor.DTO 805 - Crosswind Landing Performance - This DTO was not accomplished as thecrosswinds were not of sufficient magnitude to meet the minimum requirements ofthe DTO.

DETAILED SUPPLEMENTARYOBJECTIVES QDSO 317 - Collection of Shuttle Humidity Condensate for Analytical Evaluation -The datacollectionwas successful;however,some sampleswere lowervolumethanexpected. Indications are that all data were collected successfully.


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O DSO 802 EducationalActivities ThisDSO was completed.DS0 901- DocumentaryTelevision- ThisDS0 was completed.DS0 902- DocumentaryMotionPicturePhotography- ThisDS0was completed.DSO 903- DocumentaryStillPhotography- ThisDSOwas completed.DS0 904- Assessmentof HumanFactors- Datacollectionwas successfulandcomplete.

PHOTOGRAPHICAND TELEVISIONANALYSISLAUNCHDATAANALYSIS

On launchday,24 videoswerereceivedand evaluated,and no anomalieswerefound. Duringthe courseof themission,all 57 of theexpectedlaunchfilmswere receivedand analyzed.No in-flightanomalieswerenoted.ON-ORBITDATAANALYSIS

The crewobtainednumerousphotographsof theET afterseparationin supportofDTO 312. One of thedivotsin the insulationhas beenidentifiedas an anomaly.O Thisanomalyis discussedin theExternalTanksectionof thisreport.LANDINGDATAANALYSIS

Eightlandingvideoswere receivedforevaluationaboutthreehoursafterlanding.No anomalieswerenoted. The landingvideosdid containexcellentcoverageof thedrag chutedeploymentand fullinflation.The landingvideos


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ATABLE I.- STS-47 SEOUENCEOF EVENTS

Event Description Actualtime,G.m.t.APU activation APU-I GG chamberpressure 256:14:18:10.67

APU-2 GG chamberpressure 256:14:18:13.10APU-3 GG chamberpressure 256:14:18:14.99 'SRB HPU activation LH HPU system A start command 256:14:22:32.110LH HPU system B start command 256:14:22:32.270RH HPU systemA start command 256:14:22:32.430RH HPU system B start command 256:14:22:32.590Main propulsion Engine 3 start commandaccepted 256:14:22:53.458'System start Engine 2 start commandaccepted 256:14:22:53.583Engine 1 start commandaccepted 256:14:22:53.693SRB ignition command SRB ignitioncommand to SRB 256:14:23:00.010(lift-off)Throttleup to Engine 3 commandaccepted 256:14:23:03.898I00percent thrust Engine2 commandaccepted 256:14:23:03.903

Engine 1 commandaccepted 256:14:23:03.893Throttle down to Engine 3 commandaccepted 256:14:23:27.89967 percent thrust Engine 2 commandaccepted 256:14:23:27.903Engine 1 commandaccepted 256:14:23:27.894Maximum dynamic Derivedascent dynamic 256:14:24:00pressure (q) pressureThrottle up to Engine 3 commandaccepted 256:14:24:00.060104 percent thrust Engine 2 commandaccepted 256:14:24:00.064Engine I commandaccepted 256:14:24:00.055Both SRM's chamber RB SRM chamber pressure 256:14:24:58.750pressure at 50 psi mid-rangeselectLH SRM chamberpressure 256:14:24:59.010

mid-rangeselect


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TABLEI.-STS-47SEQUENCEOF EVENTS(Continued)Event Description Actual time,G.m.t.

OMS-I ignition Left engine bi-prop valve Not performed - position directinsertionRightenginebi-propvalve trajectoryflownpositionOMS-Icutoff Leftenginebi-propvalvepositionRightenginebi-propvalvepositionAPU deactivation APU-3GG chamberpressure 256:14:36:10.99APU-IGG chamberpressure 256:14:37:58.88APU-2GG chamberpressure 256:14:37:00.74OMS-2ignition Rightenginebi-propvalve 256:14:59:12.1

positionLeft engine bi-prop valve 256:14:59:12.0

positionOMS-2 cutoff Left engine bi-prop valve 256:15:01:51.2position

Right engine bi-prop valve 256:15:Ol:51.3positionPayloadbay dooropen PLBDrightopenI 256:15:57:19

PLBDleftopen1 256:15:58:39positionIFlightcontrolsystemcheckoutAPU start APU-3GG chamberpressure 262:09:45:20.14APU stop APU-3GG chamberpressure 262:09:57:57.64Payloadbay doorclose PLBDleftclose1 264:09:13:54


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TABLEI.- STS-47SEQUENCEOF EVENTS(Concluded) @Event Description Actualtime,G.m.t.

Terminalarea Majormodechange(305) 264:12:47:00energymanagementMain landinggear LH MLG tirepressure 264:12:53:22 'contact RH MLG tirepressure 264:12:53:22Mainlandinggear LH MLG weighton wheels 264:12:53:23weighton wheels RH MLG weighton wheels 264:12:53:23Dragchutedeploy Dragchutedeploy1 CPVolts 264:12:53:30.9Noselandinggear NLG tirepressure 264:12:53:39contactNoselandinggear NLG WT on Wheels-I 264:12:53:39weighton wheelsDragchutejettison Dragchutejettison1 CP Volts 264:12:53:57.3Wheelsstop Velocitywith respectto 264:12:54:11runwayAPU deactivation APU-IGG chamberpressure 264:13:07:42.87APU-2GG chamberpressure 264:13:07:44.67

APU-3GG chamberpressure 264:13:07:45.76'


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' " TABLEII.- STS-47PROBLEMTRACKINGLIST

Number Title Reference Comments

STS-47-V-01 Aft Compartment Heli,m 256:07:00 G.l.t. During the initialLit, fastfill prior to recirculation pump activationConcentration Exceeded IPR 54V-0003 the aft compartment GH_ concentration peaked at 550 ppm (corrected),500 ppe Launch Comit violating the Lt'C liml[ for OV-105 of 500 ppm. After transition to:criteria (Lt'C) Lilit replenish, the concentration decayed to 75-100 ppm_ below the limit ofof 150 ppm.

KSC: Troubleshooting in work.STS-47-V-02APU 3 Fuel Test Line 256:08:45 G.m.t. APU 3 test linetee_mrature2 (V46T0384A)trended low duringprelaunch.

Teeperature Low IM47RF04 prelaunch activities. The temperature reached as low as 46 F. The(Prelaunch) PR-APU-A0004 LCC lower limit was waived from 48 F to 43 F.STS-47-V-03 RCSThruster L3A Failed 256:14:33 O.n.t. Thruster L3A failed off when first commanded to fire after ET

Off IM47RF01 separation. Both oxidizer and fuel flowed, but chamber pres sure onlyPR LP03-14-0361 reached 8 psia. Most probable failure mode is partial (pilot only)flow through the oxidizer valve with full fuel flow.KSC: Will horoscope the pressure transducer prior to thruster

replacement. Spare assets available on shelf.STS-47-V-04 SSME 11a_ Inlet Pressure 256:14:25 O.l.t. The pressure transducer failed off-scale low. Troubleshooting

Transduce_ Fall IM47RF02 complete.(V41PII00C) PR-MPS-0243 KSC: Perform leak and electrical checks. Remove and replacetransducer. Spare transducer on the shelf.t,_ STS-47-V-05 Water SprayBoiler(WSB) 256:14:34G.m.t. Duringascent,W_B I did not spray until the APU I lubrication oil_O I Over Temperature IM47RFI3 temperature reached 280F. Once cooling started, the wsB overcooledPRRYD-5-03-0094 (to 23EF), then operated nominally. The File IX in-flight checkoutlimit of 275F was vio lated.

KSC: 3SC will request hot f lush.STS-47-V-06 Oxygen Tank 4 Heater 256:15:30 O.I.t. Oxygen tank 4 control pressure Indicated off-scale low. The crewControl Pressure Off-Scale IM47RF05 checked the tank 4 controller circuit breaker and found it closed. Th(

Low IPR-54-0007 crew cycled the circuit breaker 10 times, but the controller outputcould not be recovered. Oxygen tank 4 works with oxygen tank 3 as apaired sat. Normal readings returned five minutes prior to touchdown(at TAEM) .KSC: KSC will troubleshoot con trol ler, wiring, and transducer.

STS-47-V-07 WSB 3 FailedTo Cool on 256:14:34G.m.t. WSB 3 failedto cool on the A controller. Switched to B controller an,Controller A IM47RF13 cooling did not occur until 311F; consequently, APU 3 was shutdownPR-HYD-5-03-0094 before WSB 3 was turned off. WS8 3 remained on for two more minutes.

The WSB sprayed and cooled the APU 3 lubrication oil. Good FCScheckout on APU 3 . WSB 3 cooled normally on both controllers, andthere was good cooling on B controller during entry.

STS-47-V-08 Fuel Cell Water Relief 256:18:09 G.m.t. The fuel cell water relief line temperature dropped below the normalLine Tee_eraturo Erratic IPR 54V-0008 heater activation setpoint of 70F. In addition, the fuel cell 3water relief line temperature appeared to be. dropping with the relief

line tee_erature. _bst likely cause was a s_]_ll amount of waterdribbling through the fuel cell 3 water relief valve, resulting in atemperature decrease. Spare relief valve panel is available at KSC.No water was visible during postflight walkaround.KSC: Perform troubleshooting.


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TABLE IX.- STS-47PROBLEMTRACKINGLIST

Number Title Reference Comments

STS-47-V-09 RCS Thruster LSD Ras Low 259:20:i5 O.m.t. RCS thruster LSD chamber pressure was consistently low (85 psia vs.Chamber Pressure IH 4TRF03 II0 psia nominal). A 5-second hot fire of _he thruster did not improve

PR-LP03-14-0362 the chamber pressure. Analysis shows that mixture ratios are very low.Following FCS checkout, chamber pressure recovered to nominal levels{I03 psi) with some intermittent pulses below nominal.i KSC: Remove and replace thruster.

STS-47-V-10 _8 2 Regulator Outlet 256:14:24 O.m.t. During ascent, the GN2 regulator outlet pressure reading stuck at itsPressure Erratic PR-HTD-5-03-0093 initial reading _41ilethe actual pressure decreased. The readingunstuck and jum_d to the lower correct reading. Troubleshooting willinclude cycling the regulator 10 times (we. the usual 1 cycle).KSC: Perform troubleshooting.

STS-47-V-11 KU-BOnd Range Rate/Azimuth 259:03:20 G.e.t. The crew reported that the tens digit of the Ku-Band range rate/azimuthDisplay Failure XPR 54v-0013 digital display was blank. A lamp test was performed and the LEDLN471_07 saints all illuminated.

PR COM-0047 KSC: Remove and replace indicator. Spare hardware on the shelf.STS-47-V-12 Left-Rand Outboard Tire 261:15:00 G.m.t. Both left-hand outboard tire sensors (1 and 2) have an excessive bias

Pressure Bias XPR 54V-0014 with respect to the new calibration curve used. All other tireIM4?RF04 pressure measurement biases are within specifications. KSC inspectedsensors and recorded actual tire pressures. Data review in progress.

to KSC: Pressure transducer will be pulled and sent to Rockwell-Downey0 for analysis.STS-47-V-I]RudderSpeed_rakeTPS 263:04:49G.m.t. The crawtransmittedvideoshowinga portionof thethermalbarrierDisplaced 06:04:26MET whichappeared tobe protruding.The debondedportionwas describedasextending1.5inchesfromthestructurehingellneto 3 inchesawayat

the trailing edge.STS-47-V-14 Fuel Cell 02 Flowmeter 262:12:48 G.m.t. Erratic flow reading occurred during entry (about 2 to 3 minutes afterErratic IPR 54V-0016 start of TAEM), lasted approximately 10 minutes. Fly as is.IM47RFI4STS-47-V-I5 Humidity Sensor Failure 264:13:13 O.m.t. Humidity reading stuck at constant reading. Same signature as on49RF17-010 STS-49. Didn't respond to postfllght humidity changes. Postflight

PR ECL-268 inspection revealed that the sensor still had factory wrapping on it.Wrapping removed and sensor checked out satisfactorily. Fly as is.

STS-47-V-16 APU 1 Drain Line 257:00:23 G.m.t. The APU 1 drain line temperature 2 measurement consistently decreasedTemperature 2 Low IN 47RF06 to 47F before the thermostat turned on the heater. The FDA limitIPR54V-0023 of 4$oFwasTMBU'dto 45Ffor theremainderof the flight.KSC: Willperforma detailedinspectionof theheatersystem.

STS-47-V-17-ZStarTrackerself-Test1256:18:24O.m.t. The -Z startrackerfailedthefirsttwoself-testsduringFailure XPR 54V-0021 post-insertionactivation.Subsequentself-testspassed.AnIN 47RF08 additional self-test failure occurred later in the flight. The star

tracker operated no'nelly throughout the mi._sion.KSC: WiI1 perform series of self-tests to troubleshooting.

. .


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O" ' ' TABLE II.- STS-47PROBLEMTRACKING LIST

Number Title Reference CommentsSTS-47-V-18 CCTV D Jitter 260:23:00G.m.t. Pan and tilt motionof the camerawas slow. Motion shouldbe

1.2 deg/secand observedmotion was between0.3 and 0.5 deg/sec.Cameraand pan/tiltassembliesand cableswill be sentback to vendorfor analysis.STS-47-V-19 TACANBearing Excursion 264:12:46:30 G.m.t. During entry, the TACANbearing indication experienced a 40 excursionII_t 54V-0029 for 13 seconds.IH4_11 KSC: Wil l perform ground testing using bearing sinuJlator. Removeand replace TACAN2, and return to vendor.STS-47-V-20 WSB1 Regulator Outlet 258:00:00 G.m.t. Regulator outlet pressure steadily increased throughout the flight,Pressure Leakage PR-HYD-5-03-0091 indicating leakage past the regulator.STS-47-V-21 FES TemperatureExcursions264:12:00G.m.t. Severaloscillationsin the FES outlettemperaturewere seen afterFESstart up. Similarsignatureseen on STS-49. Temperaturesensorswererepacked following STS-49.STS-47-V-22 Orbiter Pulled to Left 264:12:53:30 O.m.t. Following drag chute de-reef and prior to nose landing gear tiresAfter Drag Chute Disreef touching down, the Orbiter began to veer to the left.STS-47-V-23 Air-to-Ground I/Air-to- 260:00:00 O.m.t. During the mission, the crew noticed some crosstalk from Air-to-GroundGround 2 Cross Talk 1 to Air-to-Ground 2 voice channels.STS-47-V-24 GalleyPackageIn-Place 261:00:00G.m.t. The galleypackageIn-placemicroswitchwas very stickyduring in-t_k-_ Switch flightoperations.KSC: Will return galley to JSC.STS-47-V-25 MissionSpecialist] 256:14:20G.m.t. Duringprelaunchoperations,the MissionSpecialist3 (MS3)launchLaunchEntry SuitOxygen entry suit oxygenhose became disconnected.MS3 couldnot relocatean4Hose reconnect hose.STS-47-V-26 Chin PanelThermalEffects264:13:00G.m.t. The chin panel gaps expanded. Similarsignatureseenon STS-49.PR-FWD-0452 Chin panel removed,and gap fillerremovaland replacementin work.


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TABLEIll.-SPACELAB-JEXPERIMENTSLISTING

EXPERIMENTTITLE I EXPERIMENTSPONSOR OSponsoredby NASAMaterialSciences SpaceAccelerationMeasurementSystem Dr. RichardDeLombardLewisResearchCenterFluidTherapySystem:In-flight Dr. CharlesLloydDemonstrationof the SpaceStation JohnsonSpaceCenterFreedomHealthMaintenanceFacilityFluidTherapySystemMagneticResonanceImagingAfter Dr.AdrianLeBlancExposureto Microgravity MethodistHospital,Houston,Tx.

Life SciencesProteinCrystalGrowth Dr. CharlesBugg,Universityof Alabama,BirminghamAutogenicFeedbackTrainingEquipment:Dr. PatriciaCowingsA PreventativeMethodforSpace AmesResearchCenterMotionSicknessBone CellGrowthand Mineralization Dr. NicolePartridgein Hicrogravity St.LouisUniversityMedicalSchoolEffectsof Weightlessnessin the KennethA. SouzaDevelopmentof AmphibianEggs AmesResearchCenterFertilizedin SpaceLowerBodyNegativePressure:Counter-Dr. JohnCharlesmeasurefor ReducingPostflight JohnsonSpaceCenterOrthostaticIntolerancePlantCultureResearch(Gravity, Dr. AbrahamKrikorianChromosomes,and OrganizedDevelop- StateUniversityof New Yorkmeritin AsepticallyCulturedPlant StonyBrookCells)


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TABLEIII.-SPACELAB-JEXPERIMENTSLISTING

O EXPERIMENT TITLE EXPERIMENT SPONSOR HighTemperatureBehaviorof Glass Dr.NaohiroSoga(M-8) KyotoUniversityGrowthof SiliconSphericalCrystals Dr. TatauNishinaga'. and SurfaceOxidation(M-9) Universityof TokyoStudyon Solidificationof Immiscible Dr. AkihikoKamioAlloy(M-10) TokyoInstituteof TechnologyFabricationof Very-Low-Density,High- Dr. TomooSuzukiStiffnessCarbonFiber/Aluminum TokyoInstituteof Technology

HybridizedComposites(M-II)Studyon theMechanismsof LiquidPhaseDr.ShiroKoharaSintering(M-12) ScienceUniversityof TokyoFabricationof SI-As-Te:NiTernary Dr. YoshihiroHamakawaAmorphousSemiconductorin Micro- OsakaUniversitygravityEnviaronment(M-13)Gas-Evaporationin LowGravityField: Dr.NobuhikoWadaCongelationMechanismof MetalVaporsNagoyaUniversity(M-14)DropDynamicsin SpaceandInterferenceDr.TatsuofamanakawithAcousticField(M-15) NationalAerospaceLaboratoryStudyof BubbleBehavior(M-16) Dr. HisaoAzumaNationalAerospaceLaboratoryPreparationof OpticalMaterialsUsed JunjiHayakawa

O inNon-VisibleRegion(M-17) GovernmentIndustrialResearchInstituteMarangoniInducedConvection in Dr. ShintaroEnyaMaterialsProcessingUnderMicro- HeavyIndustriesgravity(M-18)Solidificationof EutecticSystem Dr.AtsumiOhnoAlloysin Space(M-19) ChibaInstituteof Technology


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TABLEIII.-SPACELAB-JEXPERIMENTSLISTING

EXPERIMENTTITLE EXPERIMENTSPONSOR @LifeSciences(Continued)Studieson the Effectsof MicrogravityDr. AtsushigeSatoon theUltrastructureandFunctions TokyoMedicalandDentalUniversity

of Cultured Mammalian Cells (L-5) ,_The Effect of Low Gravity on Calcium Dr. Tatsuo SudaMetabolism and Bone Formation (L-7) Showa UniversitySeparation of the Animal Cells and Dr. Tokio YamaguchiCellular Organella by Means of Free Tokyo Medical and Dental UniversityFlowElectrophoresis(L-8)GeneticEffectsof HZE and Cosmic Dr. MituoIkenagaRadiation(L-9) KyotoUniversitySpaceResearchon PerceptualMotor AkiraTadaFunctionsUnderZeroGravity NationalAerospaceLaboratoryCondition(L-10)Studyon theBiologicalEffectof Dr. ShunjiNagaokaCosmicRadiationand theDevelopmentNationalSpaceDevelopmentAgencyofof RadiationProtectionTechnology Japan(L-II)CircadianRhythmof Conidiationin Dr. YasuhireMiyoshiNeurosporaCrassa(L-12) Universityof Shizuoka


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NSTS-08279 - STS-47 Space Shuttle Mission Report_A Headquarters CA4/J. williams ESJ/P. Serna BARR/H.Jones Darryl Strickland James R. WomackQP/8. Greenly CB/D. Leastma (10} ES6/C. W. Norris (2} BARR/R. Herman P.O. Box 1940 JPL/233-307QP/R. Perry CB/K.. Colgan ET/C. A. Graves, Jr. (8] Era/Hamilton Standard North Highlands, CA 4800 Oak Grove DrQT/N. Greenfield CB/T. Henricks ET3/T. Farrell _31/NASDA13) 95660-8940 Pasadena, CA91109MCF/D.Hedin I_/Library EKiTDSDLibraryNOJ/C. Perry DA1S/D. Nelson DJ/J. W. Seyl (2} RA/R. A. Colonna (2} Ames Research Center James V. ZimmermanDAJ/S. G. Bales GA/T. W. Holloway _qlite Sands Test Facility Noffett Field, CA 94035 NASAEuropean RapGoddard Space Flt Ctr DA3/R. K. Holkan GN/D. C. Schultz P.O. Drawer _ 233-17/J. Hart c/o American Embassy300/R. C. Bauman DAS/R. Logier JL4/R. L. Squires Las Cruces, _UI88004 APe NewYork, NY09777700iT. E. Nuber DAB/Library JMB/Library {3} C. Woodland, Prog. Mgr.710//W. Mayer DF/J. Knight MJ/T. R. Lee 12} External Distribution SPARAerospace Limited Capt. J. Bahling730/E. $. Powers DFT/P. Cerna NA/C. S. Harlan Hr. Willis M. Hawkins 9445 Airport Road 6555 ASTG/S_tSP730.1/J. P. Young DF?2/_. Carelock ND/N. C. Perry Senior Advisor Brampton, Ontario, Cape Canaveral AFS, FL.400/V. Weyers DG/J. A. Wagoner ND3/L. Lewsllan Lockheed Corporation Canada, L6F4J3 32925100/P. T. Burr _4/D. Rickerl NS/D. W. Whittle P.O. Box 551302/W. F. Bangs _4/Lead FAO PA/R.L. Barry Burbank,CA 91520 A.S. Jones (2} LESC-Houston313/R. Marriott DH411/E. B. Ptppert PA/J. R. Garmm SPARAerospace Limited BO8/P. Davis130/3. Katz DH/J. F. Whttely PT3/S. Morris NASA-LewisResearch Center 9445 Airport Road C07/LESCLibraryDH45/M.LeBlanc SA/C. L. Huntoon Cleveland, OH. 44135 Brampton, Ontario C12/D. HarrisonKSC _6/3. L. Clement SA/W.D. Womack Attn:333-1/T. Fuller CanadaL6F4J36 CI2/R.W. Frlcke(I0)Li"-brary-D{20copies} DG47/SImSup's SD/S.L. Pool C87/D.WeisslngerMK/B.N. Shaw DG66/H.Lampazzl SD2/R.D.Blllica RussellA. Lateen J. MiddlatonLSO-420/W. K. Hollts DG67/C. Noede SD24/D. A. Bushing Mail Stop 4A SPARAerospace Limited GEGovernment Services_/J. C. Harpold SD4/N. Clntron Charles Stark Draper Lab. 1700 OrmontDrive 1050 Bay Area Blvd.MSFC I_2/J. R. Montalbano SD5/3. Charles 555 Technology Square Weston, Ontario, Houston, TX 77058CN2----2D/Respository(30} EH22/W.Hollister SE/J. H. Langford Cambridge, MA02139 Canada MgL2W7 Attn: A. VerrengiaEP51/3. Redus (5) EA/H. O. Pohl SN15/D. PittsEE31/P.Hoag 15) EC/W.E. Ellis SP/C.D. Perner(53 Mr. Ira GrantHedrick N. Parmet TRWFA51/S.P.Sauchier EC/F.H. Same TA/C.H. Lambert PresidentialAssistant 5907SunriseDrive I SpacePack DriveJA01/J.A. Downey EC3/D.F. Hughes TC3/J.Love for CorporateTechnology Fairway,Kansas 66205 Rll/1850- L. StytleSAI2/O.E. Henson EC2/M.Rodrlguez TC3/T.Bruce OrusaanAerospaceCorp RedondoBeach,CA 90278EC4/L.O. Casey TJ/L. E. Ball Bethpage,NY 11714 R. PetersonLangley ResearchCenter EC3/E.Winkler TJ2/G.W. Sandars 3303SanGabriel HQ AFSPACECOM/DOSLTechnicalLibrary/ EC3/H.Rotter(2} TM2/G.Nield {2} Dr. SeymourC. Hi_mel Clearwater,FL 34619 Bldg I Stop 7Mall Stop 185 EC3/N.Fagot VA/D.N. Germany 12700LakeAvenue,|1501 PetersonAFBEC6/J.W. McBarron VA/P.C. Olynn Lakewood,OH 44107 AerospaceCorporation ColoradoSprings,Co 80914Rockwell-Downey EE/J.Griffin VA/W. H. Taylor P.O. Box 92957 Attn: Capt.S. M. YoungAD75/DataManagement(50)EE2/H.A. Vang VF/D.W. Camp Mr. John F.McDonald Los Angeles,CA 90009EE3/P.Shack VF/E. R. Hischke Vice President-TechnicalAttn: W. Smith,M5/619 LockheedAdvancedRockwell-Houston EE6/L. Leonard VF2/W. O. Gaylor Services Davelopment Co.RI2A-130/J.C. Snowden EE6/R.Nuss VF2/R.Brasher TigerAir,Inc. McDonnellDouglas-HoustonP.O. Box 250RI2A-130/J.P. Shea EET/M.D. Schmalz VF3/M.T. Suffredlnl(13) 3000NorthClaybournAve T3A/A.D. Hockenbury Sunland,CA. 91041ZC01/C.Ritrlvl EET/J.C. Dallas VG/F. Littlet0n Burbank,CA 91505 Attn:D. Urla D/7212,R20A/J.Woodard EK/I.Burtzlaff VG/H.Kolkhorst T. Myers,Sys Tech, Inc. B375,P/D6R20B/R.Pechacek ET5/J.A. Lawrence VK/E.E. Wright Dr. JohnO. Stewart 13766So.HawthorneBlvd.RI6H/K.M. Rahman EG/J.Thibodeau VM/C.Crltzos Manager,Officeof Hawthorne,CA 90250 R. BirmanZC01/J. Woodall EG2/K. D. Frank VM/J. W. Mistrot Planning and Budget General Electric Co.ZC01/W.Scott EG3/R.Barton VM/K.E. Kamlnskl(25) TVA E 6C9 D. Molgaard Space DivisionEG3/P.Remora VP/C.Mccullough(3) 400 CommerceAvenue 2525 Bay Area Blvd. P.O. Box 8555JSC EG3/S.Dorry VPI2/D.Fitts Knoxville,TN 37902 Suite620 Philadelphia,PA 19101_A. Cohen EES/W.N. Trahan VP5/J.Goodman Houston,TX 77058AC/D.A. Nebrig EP2/H.J. Brasseaux VR/D.D. Ewart TRW Headquarters,SMCAC5/J.W. Young EP2/L.Jenkins _/L. G. williams Houston,TX 77058 L.R. Adkins/IBMBldg Attn.: SMC/CULOAP3/J.E. Riley (4) EP5/T.L. Davies _/L. D. Austin Attn: C. Paterson/H5 Mall Code6206 MajorD. JoslynAP4/8.L. Dean (3) ER/W.W. Guy WE/R.D. White 3700Ba_Area Boulevard LosAngelesAF BaseLA/W.L. Draper ES/D.C. Wade WG/W. J. Moon JohnWilli_ms Houston,_rx77058 P.O. Box 92960BY4/HistoryOffice(2) ES/W.G. McMullen (2) ZR/Lt.Col. J.McLaroy 1995 FerndalePlace LosAngeles,CA 90009-2960CA/S.A. Hawley ES/J.A. Smith ZRI2/J.Ao Yannie ThousandsOaks,CA 91360CA4/R.Filler ES3/Y.C. Chang BARR/J.WhiteNotify VF2/R. W. Fricke |713-483-33133 of any correction, additions, or deletions to this list.

sts-47 space shuttle mission report

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